Self-propelled, vaned missile

ABSTRACT

A self-propelled vaned missile, designed to be fired by means of a launching tube and wherein the vane system comprises at least three fins articulated onto pins disposed at the rear of the missile, the pins being perpendicular to the axis of the missile. It is new in that the fins of the said vane system are double fins, each having blades which are joined at their hinged end by a bridge and equipped with spacing springs. These springs exert on the fins a force greater than the resistance which the air exerts on them in the course of the missile&#39;&#39;s advance, and cause the open out of the said rear fins towards the front as soon as the missile has left the launching tube.

United States Patent Rusbach [54] SELF-PROPELLED, VANED MISSILE [72]Inventor: Maurice Rusbach, Geneva, Switzerland [73] Assignee: SarmacS.A., Geneva, Switzerland [22] Filed: Nov. 19, 1970 [2!] Appl. No.:91,031

[451 Sept. 12, 1972 Primary Examiner-Benjamin A. Borchelt AssistantExaminer-James M. Hanley Attorney-Young & Thompson [57] ABSTRACT Aself-propelled vaned missile, designed to be fired by means of alaunching tube and wherein the vane system Comprises at least three finsarticulated onto pins disposed at the rear of the missile, the pinsbeing perpendicular to the axis of the missile. It is new in that thefins of the said vane system are double fins, each having blades whichare joined at their hinged end by a bridge and equipped with spacingsprings. These springs exert on the fins a force greater than theresistance which the air exerts on them in the course of the mis'silesadvance, and cause the open out of the said rear fins towards the frontas soon as the missile has left the launching tube.

12 Claims, 8 Drawing Figures [52] US. Cl. ..244l3.27, 102/34.1, 102/37.1[51] Int. Cl. ..C06d 1/04, F42b 13/32 [58] Field of Search ..244/3.24,3.27, 3.28; 102/34.1, 37.1

[56] References Cited UNITED STATES PATENTS 1,879,840 9/1932 Brandt..244/3.29 X I 3,114,318 12/1963 Barnes et al. ..-102/34.1 3,098,4467/1963 Jasse ..244/3.28 FOREIGN PATENTS OR APPLICATIONS 1,351,42212/1963 France ..244l3.28

PNENTEDSEP 12 m2 sum 2 BF 3 FIG. 4

h Z Z M n 5 m U W 1 SELF-PROPELLED, VANED MISSILE Many missiles,particularly self-propelled missiles which are fired by means of alaunching tube, are equipped with a vane system which opens out once themissile has left its launching tube.

In order to ensure the greatest possible firing accuracy, it isadvantageous for such a vane system to open out rapidly as soon as themissile has left the launching tube.

The invention concerns a self-propelled vaned missile, the vane systemof which comprises at least three fins hinged onto pins which aredisposedfat the rear of the missile, the pins being perpendicular to theaxis of the missile. The missile is distinguished by the fact that thefins of the said vane system are double fins, each having blades whichare joined at their hinge end by a bridge and equipped with spacingsprings which exert on them a force greater than the resistance whichthe air exerts on them in the course of the missiles advance, thesprings being adapted to open out the said rear fins towards the front,as soon as the missile has left the launching tube.

Such a missile preferably has, at the rear, a coaxial nozzle aroundwhich the said fins of the vane system can be mounted. In the foldedback condition the free end of the fins may bear against the rear end ofthe nozzle and, once opened out, their end which is hinged around thesaid pins may bear against the body of the missile or the front end ofthe nozzle.

The hinge pins of the fins of the vane system may be mounted on prongsbelonging to a collar fixed to the nozzle, near the end where it isfixed to the body of the missile.

The spacing springs of the said fins may partially surround or be woundaround the hinge pins of the fins. Theactive limbs of these spacingsprings preferably bear, on the one hand against the nozzle and on theother hand against the corresponding fin. The force of these returnsprings will preferably be at least twice the resistance of the air tothe advance of the missile.

The fins may have a U-shaped cross-section and the blades of these finsmay possibly diverge from one another from the base of the U towardstheir free ends. Once .opened out, the vane system preferably representsmore than twice the diameter of the missile proper, and it may comprisea device for locking the fins in their opened out position.

An embodiment of a vaned missile according to the invention and twomodifications relating to details are shown by way of example in theaccompanying drawings, in which:

FIG. 1 is an elevation of the whole missile.

FIG. 2 is a view of part of the missile, on a larger scale and partly inlongitudinal section.

FIG. 3 is a section on the line III-III in FIG. 2.

FIG. 4 is a view of part of the missile, similar to FIG. 2 and showingthe vane system opened out.

FIG. 5 is a section on the line V-V in FIG. 4.

FIGS. 6 and 8 are partial views similar to FIG. 2, showingmodifications, and

FIG. 7 is a section on the line VII-VII inFIG. 6.

The missile shown in the drawings is a self-propelled missile, having anexplosive charge in front at 1 and a propulsive charge at the rear at 2.The propulsion gases escape through the coaxial nozzle 3, on which ismounted a collar 4 equipped with four pairs of prongs 5, each of whichhas a pin 6 passing through it, onto which the fins 7 of the vane systemare hinged. The fins 7 are double fins of U-shaped cross-section. Solong as the missile is in the launching tube, they are folded back ontothe nozzle 3 against the action of the return springs 8. The blades ofthe fins 7 are equipped with a stiffening rib 9, and the ends 10 of thefins 7 hinged around the pins 6 are shaped so that, when the vane systemis opened out, they bear against the collar 4, surrounding the front endof the nozzle 3, at the place where the latter is screwed onto the rearend of the body of the missile (see FIGS. 4 and 5).

The return springs 8 are spacing springs of the safetypin type, whichare wound around the pins 6, so that their median bent back portion 11bears against the nozzle, while their two free ends 12 bear against thelower face of the corresponding fin 7.

In the modification shown in FIGS. 6 and 7, the spacing return springs13 only partially surround the hinge pins 6 of the fins 7. Their median,bent back portion 14 bears against the nozzle 3 and their free ends 15are bent back below the lower edge of the blades of the fins 7.

As shown in FIG. 8, the free bentback ends 15 of the spacing springs 13may also engage in orifices 16 in the said blades of the fins 7. In thiscase, it will not be necessary for them partially to surround the hingepin 6 of the fins 7. The blades of the double, U-shaped fins shown inthe drawings may diverge obliquely from one another from the base of theU towards their free ends. The opening out of the fins of the vanesystem may, on the other hand, be limited as desired, by modifying theconfiguration of their end 10 bearing against the body of the missile orthe front end of the nozzle, when the vane system is opened out. Toensure that the missile is really stable, the diameter of the vanesystem, once opened out, should preferably be over twice the diameter ofthe missile proper.

In order to make the vane system system open out rapidly and to preventit from folding back partially by the effect of the resistance set up bythe air, the force of the return springs 8 13 should preferably be atleast twice the resistance which the air exerts on the fins during themissile s advance.

The return springs 8 13 are in all cases housed between the blades ofeach of the fins. The latter are not exposed, either in the folded backor the opened out state, to the dust from the propulsion gases escapingfrom the nozzle.

The vane system as described is perfectly suitable for missiles withsingle stage propulsion, where combustion is practically over when themissile leaves the launching tube and where the velocity is of the orderof to 200 m/sec. However, in the case of the missile being equipped withsecond stage propulsion, which comes into action when the missile hascovered, e.g., a distance of 50 m, after leaving the launching tube, inorder to give it a wider range, it is advisable to provide a device forlocking the fins of the vane system in the opened out position, in orderto prevent any tendency they may have to fold back against the nozzle bythe effect of the acceleration which takes place, when the second stageof propulsion of the missile is fired, in cases where the return springswould not be strong enough to resist the acceleration efiect.

As an auxiliary effect the prongs of the collar 4 allow the rear portionof the missile to be centered in the launching tube.

In one modification the prongs 5 of the collar 4 could, in the place ofthe orifice provided to give passage to the pin 6, have nipples facingone another, on which one could mount a hollow hinge pin which couldpossibly be integral with the fin 7. Or, alternatively, the prongs 5could contain recesses into which the ends of the said pin 6 wouldengage. In the case of the fins being made of plastics, for example, thepin 6 could be omitted altogether and replaced by a boss provided eitherwith two coaxial orifices for the insertion of the said nipples of theprongs 5, or with coaxial projections engaging into the said recesses inthe prongs 5 of the collar 4.

The collar 4 could even be omitted altogether and the prongs 5 weldeddirectly onto the nozzle 3 or made in one piece therewith.

When the fins 7 are made of sheet metal, which is cut out and bent, theyare made integrally with the bridge connecting their two blades. Thebridge gives them rigidity, which is further increased when the saidblades have a longitudinal rib 9 extending below the bridge 17 (see FIG.2). The spacing between the blades of the fins 7, corresponding to thewidth of the bridge 17, ensures that they are mounted stably on the pins6 passing through the two orifices in their blades, thus preventing anywobbling of the fins.

In the FIG. 2 embodiment, the end of the fins 7, when at rest, isopposite the free end of the nozzle 3. However, the end of the fins 7,when at rest, may be beyond the free end of the nozzle 3, as shown inFIGS. 6 and 8.

The vane system described has the advantage that it can be housed in avery small space, as is the case when the diameter of the launching tubeis hardly any larger than that of the nozzle of the missile.

Apart from the above-mentioned advantage, the vane system described isdistinguished by the simplicity of its construction, its lightness andits relatively low cost. The number of fins may be increased to enhancethe stabilizing effect, and the obliqueness of the blades of the finscan be modified as desired. On the other hand, the air lag of this typeof vane system, when made of pressed sheet metal, may be less than thatof vane systems with thicker fins, which minimizes the loss of range dueto the aerodynamic braking of the vane system. It should further benoted that the double fins may also have lateral flaps at the ends, thusfurther enhancing their stabilizing action.

I claim:

l. A self-propelled vaned missile, designed to be fired by means of alaunching tube and wherein the vane system comprises at least three finsarticulated onto pins disposed at the rear of the missile, said pinsbeing perpendicular to the axis of the missile, characterized in thatthe fins of the said vane system are double fins, each having bladeswhich are joined at their hinged end by a bridge and equipped withspacing springs which exert on them a force greater than the resistancewhich the air exerts on them in the course of the missiles advance,these springs being adapted to open out the said rear fins towards thefront as soon as the missile has left the launching tube, said finshaving tw blades each a d havin a U-sha ed cm s sectio 2. Aself-propelled vane d missile accord mg to claim 1, characterized inthat the blades of the said fins have a longitudinal rib extending belowthe said bridge.

3. A self-propelled vaned missile according to claim 1, characterized inthat the said fins are made of sheet metal which is cut out and bent andare made integrally with the said bridge which joins their blades attheir hinged end.

4. A self-propelled vaned missile according to claim 1, characterized inthat the blades of the said fins diverge obliquely from one another fromthe base of the U towards their free end.

5. A self-propelled vaned missile according to claim 1, characterized inthat it comprises, at the rear, a coaxial nozzle around which aremounted the fins of the vane system.

6. A self-propelled vaned missile according to claim 5, characterized inthat the fins of its vane system are shaped so that their free end bearsagainst the rear end of its nozzle in the folded back condition.

7. A self-propelled vaned missile according to claim 5, characterized inthat the fins of its vane system are shaped so that their end which ishinged around the said pins bears against its body in the opened outconditron.

8. A self-propelled vaned missile according to claim 5, and a collarfixed to the nozzle of the missile, at the end where it is fixed to thebody of the missile, said pins being mounted on prongs on said collar.

9. A self-propelled vaned missile according to claim 8, characterized inthat the active limbs of the said spacing springs bear both against thenozzle and against the corresponding fin.

10. A self-propelled vaned missile according to claim 9, characterizedin that the said spacing springs have legs interconnected by at leastone loop wound at least partially around the said hinge pins of thefins.

1 l. A self-propelled vaned missile according to claim 1, characterizedin that the said spacing springs are housed between the blades of eachof the fins.

12. A self-propelled vaned missile according to claim 1, characterizedin that the force of the said springs is at least equal to twice theresistance which the air exerts on its fins in the course of itsadvance.

1. A self-propelled vaned missile, designed to be fired by means of alaunching tube and wherein the vane system comprises at least three finsarticulated onto pins disposed at the rear of the missile, said pinsbeing perpendicular to the axis of the missile, characterized in thatthe fins of the said vane system are double fins, each having bladeswhich are joined at their hinged end by a bridge and equipped withspacing springs which exert on them a force greater than the resistancewhich the air exerts on them in the course of the missile''s advance,these springs being adapted to open out the said rear fins towards thefront as soon as the missile has left the launching tube, said finshaving two blades each and having a U-shaped cross section.
 2. Aself-propelled vaned missile according to claim 1, characterized in thatthe blades of the said fins have a longitudinal rib extending below thesaid bridge.
 3. A self-propelled vaned missile according to claim 1,characterized in that the said fins are made of sheet metal which is cutout and bent and are made integrally with the said bridge which joinstheir blades at their hinged end.
 4. A self-propelled vaned missileaccording to claim 1, characterized in that the blades of the said finsdiverge obliquely from one another from the base of the U towards theirfree end.
 5. A self-propelled vaned missile according to claim 1,characterized in that it comprises, at the rear, a coaxiAl nozzle aroundwhich are mounted the fins of the vane system.
 6. A self-propelled vanedmissile according to claim 5, characterized in that the fins of its vanesystem are shaped so that their free end bears against the rear end ofits nozzle in the folded back condition.
 7. A self-propelled vanedmissile according to claim 5, characterized in that the fins of its vanesystem are shaped so that their end which is hinged around the said pinsbears against its body in the opened out condition.
 8. A self-propelledvaned missile according to claim 5, and a collar fixed to the nozzle ofthe missile, at the end where it is fixed to the body of the missile,said pins being mounted on prongs on said collar.
 9. A self-propelledvaned missile according to claim 8, characterized in that the activelimbs of the said spacing springs bear both against the nozzle andagainst the corresponding fin.
 10. A self-propelled vaned missileaccording to claim 9, characterized in that the said spacing springshave legs interconnected by at least one loop wound at least partiallyaround the said hinge pins of the fins.
 11. A self-propelled vanedmissile according to claim 1, characterized in that the said spacingsprings are housed between the blades of each of the fins.
 12. Aself-propelled vaned missile according to claim 1, characterized in thatthe force of the said springs is at least equal to twice the resistancewhich the air exerts on its fins in the course of its advance.